NACA 63(2)A-015 (naca632a015-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 63(2)A-015 (naca632a015-il) Reynolds number: 500,000 Max Cl/Cd: 72.85 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca632a015-il-500000-n5.txt Download as CSV file: xf-naca632a015-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 63(2)A-015
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.500 -0.8195 0.06447 0.06123 -0.0533 1.0000 0.0082
-14.250 -0.8588 0.05607 0.05251 -0.0566 1.0000 0.0082
-14.000 -0.8830 0.05038 0.04654 -0.0578 1.0000 0.0082
-13.750 -0.8939 0.04674 0.04275 -0.0580 1.0000 0.0081
-13.500 -0.9084 0.04272 0.03845 -0.0575 1.0000 0.0082
-13.250 -0.9160 0.03962 0.03509 -0.0566 1.0000 0.0084
-13.000 -0.9187 0.03721 0.03251 -0.0554 1.0000 0.0084
-12.750 -0.9180 0.03519 0.03030 -0.0540 1.0000 0.0084
-12.500 -0.9162 0.03331 0.02826 -0.0523 1.0000 0.0085
-12.250 -0.9151 0.03142 0.02622 -0.0504 1.0000 0.0085
-12.000 -0.9120 0.02984 0.02453 -0.0483 1.0000 0.0087
-11.750 -0.9051 0.02877 0.02340 -0.0464 1.0000 0.0088
-11.500 -0.8980 0.02765 0.02219 -0.0442 1.0000 0.0090
-11.250 -0.8906 0.02644 0.02087 -0.0419 1.0000 0.0090
-11.000 -0.8819 0.02558 0.01994 -0.0395 1.0000 0.0091
-10.750 -0.8735 0.02471 0.01899 -0.0369 1.0000 0.0092
-10.500 -0.8651 0.02399 0.01821 -0.0341 1.0000 0.0095
-10.250 -0.8581 0.02317 0.01732 -0.0310 1.0000 0.0094
-10.000 -0.8524 0.02256 0.01664 -0.0274 1.0000 0.0096
-9.750 -0.8257 0.02149 0.01547 -0.0281 0.9920 0.0098
-9.500 -0.7979 0.02057 0.01446 -0.0289 0.9826 0.0101
-9.250 -0.7679 0.01968 0.01347 -0.0301 0.9710 0.0104
-9.000 -0.7326 0.01877 0.01246 -0.0324 0.9588 0.0106
-8.750 -0.6937 0.01780 0.01142 -0.0356 0.9451 0.0112
-8.500 -0.6527 0.01693 0.01050 -0.0391 0.9299 0.0117
-8.250 -0.6147 0.01627 0.00975 -0.0419 0.9102 0.0123
-8.000 -0.5888 0.01577 0.00913 -0.0419 0.8865 0.0127
-7.750 -0.5693 0.01534 0.00856 -0.0405 0.8628 0.0132
-7.500 -0.5519 0.01493 0.00804 -0.0387 0.8433 0.0136
-7.250 -0.5343 0.01456 0.00758 -0.0369 0.8270 0.0140
-7.000 -0.5158 0.01423 0.00718 -0.0352 0.8130 0.0145
-6.750 -0.4965 0.01393 0.00680 -0.0337 0.8007 0.0154
-6.500 -0.4771 0.01363 0.00640 -0.0321 0.7897 0.0161
-6.250 -0.4566 0.01334 0.00608 -0.0308 0.7798 0.0172
-6.000 -0.4353 0.01311 0.00580 -0.0296 0.7709 0.0188
-5.750 -0.4134 0.01288 0.00554 -0.0285 0.7617 0.0205
-5.500 -0.3910 0.01267 0.00528 -0.0275 0.7537 0.0228
-5.250 -0.3682 0.01246 0.00505 -0.0265 0.7454 0.0252
-5.000 -0.3449 0.01229 0.00481 -0.0256 0.7379 0.0278
-4.750 -0.3218 0.01208 0.00459 -0.0248 0.7296 0.0302
-4.500 -0.2979 0.01194 0.00439 -0.0240 0.7220 0.0329
-4.250 -0.2745 0.01172 0.00418 -0.0232 0.7141 0.0353
-4.000 -0.2505 0.01157 0.00397 -0.0225 0.7065 0.0376
-3.750 -0.2263 0.01139 0.00376 -0.0217 0.6994 0.0397
-3.500 -0.2022 0.01123 0.00358 -0.0210 0.6916 0.0430
-3.250 -0.1776 0.01108 0.00340 -0.0204 0.6845 0.0464
-3.000 -0.1532 0.01091 0.00323 -0.0197 0.6769 0.0508
-2.750 -0.1286 0.01077 0.00306 -0.0191 0.6704 0.0559
-2.500 -0.1039 0.01060 0.00291 -0.0185 0.6632 0.0653
-2.250 -0.0800 0.01041 0.00275 -0.0177 0.6561 0.0867
-2.000 -0.0681 0.00931 0.00232 -0.0151 0.6495 0.2881
-1.750 -0.0562 0.00838 0.00207 -0.0123 0.6428 0.4705
-1.500 -0.0333 0.00819 0.00201 -0.0113 0.6364 0.5189
-1.250 -0.0088 0.00807 0.00197 -0.0106 0.6294 0.5512
-1.000 0.0153 0.00799 0.00193 -0.0098 0.6216 0.5777
-0.750 0.0397 0.00792 0.00191 -0.0090 0.6097 0.6033
-0.500 0.0640 0.00790 0.00190 -0.0082 0.5946 0.6245
-0.250 0.0885 0.00790 0.00189 -0.0074 0.5801 0.6466
0.000 0.1135 0.00791 0.00190 -0.0068 0.5699 0.6645
0.250 0.1398 0.00791 0.00190 -0.0064 0.5605 0.6742
0.500 0.1663 0.00795 0.00190 -0.0061 0.5510 0.6815
0.750 0.1926 0.00798 0.00191 -0.0058 0.5414 0.6882
1.000 0.2191 0.00801 0.00192 -0.0055 0.5330 0.6956
1.250 0.2454 0.00807 0.00194 -0.0051 0.5236 0.7024
1.500 0.2716 0.00810 0.00197 -0.0048 0.5134 0.7091
1.750 0.2977 0.00817 0.00201 -0.0044 0.5032 0.7163
2.000 0.3237 0.00822 0.00205 -0.0041 0.4929 0.7232
2.250 0.3497 0.00828 0.00210 -0.0037 0.4827 0.7308
2.500 0.3754 0.00836 0.00216 -0.0033 0.4714 0.7375
2.750 0.4006 0.00844 0.00222 -0.0028 0.4575 0.7450
3.250 0.4501 0.00865 0.00238 -0.0016 0.4246 0.7605
3.500 0.4746 0.00879 0.00248 -0.0010 0.4066 0.7688
3.750 0.4983 0.00893 0.00259 -0.0003 0.3857 0.7771
4.250 0.5429 0.00937 0.00289 0.0017 0.3347 0.7961
4.500 0.5647 0.00961 0.00307 0.0027 0.3130 0.8067
4.750 0.5871 0.00982 0.00325 0.0037 0.2954 0.8183
5.000 0.6093 0.01003 0.00346 0.0047 0.2786 0.8308
5.250 0.6311 0.01026 0.00367 0.0057 0.2615 0.8448
5.500 0.6531 0.01050 0.00389 0.0067 0.2456 0.8600
5.750 0.6761 0.01072 0.00412 0.0074 0.2335 0.8769
6.000 0.7021 0.01092 0.00436 0.0076 0.2245 0.8950
6.250 0.7313 0.01117 0.00463 0.0070 0.2155 0.9133
6.500 0.7647 0.01145 0.00492 0.0055 0.2070 0.9288
6.750 0.8002 0.01175 0.00523 0.0035 0.1993 0.9416
7.000 0.8369 0.01210 0.00556 0.0011 0.1899 0.9518
7.250 0.8728 0.01239 0.00587 -0.0010 0.1832 0.9603
7.500 0.9064 0.01273 0.00619 -0.0028 0.1754 0.9685
7.750 0.9394 0.01304 0.00652 -0.0043 0.1683 0.9750
8.250 1.0000 0.01373 0.00720 -0.0064 0.1524 0.9895
8.500 1.0301 0.01414 0.00758 -0.0075 0.1441 0.9968
8.750 1.0581 0.01458 0.00798 -0.0082 0.1322 1.0000
9.000 1.0698 0.01491 0.00829 -0.0055 0.1233 1.0000
9.250 1.0798 0.01530 0.00865 -0.0025 0.1139 1.0000
9.500 1.0861 0.01570 0.00900 0.0012 0.1058 1.0000
9.750 1.0935 0.01610 0.00939 0.0047 0.0983 1.0000
10.000 1.1014 0.01657 0.00985 0.0079 0.0912 1.0000
10.250 1.1105 0.01709 0.01036 0.0107 0.0850 1.0000
10.500 1.1209 0.01763 0.01090 0.0131 0.0794 1.0000
10.750 1.1304 0.01826 0.01153 0.0156 0.0735 1.0000
11.000 1.1413 0.01890 0.01218 0.0176 0.0684 1.0000
11.500 1.1612 0.02042 0.01372 0.0215 0.0588 1.0000
11.750 1.1706 0.02131 0.01462 0.0233 0.0550 1.0000
12.000 1.1812 0.02218 0.01552 0.0247 0.0521 1.0000
12.250 1.1911 0.02315 0.01652 0.0261 0.0497 1.0000
12.500 1.1999 0.02426 0.01767 0.0275 0.0474 1.0000
12.750 1.2102 0.02532 0.01878 0.0286 0.0458 1.0000
13.000 1.2197 0.02647 0.02000 0.0296 0.0440 1.0000
13.250 1.2281 0.02777 0.02134 0.0305 0.0424 1.0000
13.500 1.2347 0.02925 0.02286 0.0314 0.0408 1.0000
13.750 1.2419 0.03073 0.02441 0.0321 0.0395 1.0000
14.000 1.2504 0.03216 0.02593 0.0327 0.0382 1.0000
14.250 1.2570 0.03377 0.02761 0.0333 0.0368 1.0000
14.500 1.2620 0.03559 0.02949 0.0337 0.0353 1.0000
14.750 1.2650 0.03764 0.03159 0.0341 0.0341 1.0000
15.000 1.2699 0.03956 0.03359 0.0343 0.0330 1.0000
15.250 1.2740 0.04161 0.03574 0.0344 0.0320 1.0000
15.500 1.2770 0.04384 0.03805 0.0344 0.0311 1.0000
15.750 1.2782 0.04632 0.04060 0.0343 0.0302 1.0000
16.000 1.2780 0.04903 0.04338 0.0340 0.0295 1.0000
16.250 1.2764 0.05200 0.04642 0.0336 0.0286 1.0000
16.500 1.2754 0.05497 0.04949 0.0330 0.0281 1.0000
16.750 1.2735 0.05813 0.05275 0.0323 0.0276 1.0000
17.000 1.2707 0.06148 0.05620 0.0315 0.0270 1.0000
17.250 1.2661 0.06514 0.05996 0.0304 0.0266 1.0000
17.500 1.2611 0.06892 0.06384 0.0293 0.0261 1.0000
17.750 1.2549 0.07295 0.06796 0.0280 0.0257 1.0000
18.000 1.2461 0.07745 0.07255 0.0264 0.0253 1.0000
18.250 1.2362 0.08219 0.07739 0.0246 0.0251 1.0000
18.500 1.2254 0.08713 0.08242 0.0227 0.0247 1.0000
18.750 1.2120 0.09258 0.08796 0.0205 0.0243 1.0000
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